Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster

The Faraday probe and cylindrical Langmuir probe were used to characterize the downstream ion and electron spatial evolution of a 300 W class low-power Hall thruster. The time-averaged ion current density, electron energy probability function, plasma potential, electron temperature, and electron den...

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Autores principales: Xinwei Chen, Jun Gao, Zuo Gu, Ning Guo, Shangmin Wang, Sanxiang Yang, Yifan Ma, Kai Shi, Hai Geng, Hong Zhang, Yanxu Pu
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Publicado: AIP Publishing LLC 2021
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Acceso en línea:https://doaj.org/article/f54a5b782d5c42dea853981529fd96d3
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spelling oai:doaj.org-article:f54a5b782d5c42dea853981529fd96d32021-12-01T18:52:06ZSpatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster2158-322610.1063/5.0063803https://doaj.org/article/f54a5b782d5c42dea853981529fd96d32021-11-01T00:00:00Zhttp://dx.doi.org/10.1063/5.0063803https://doaj.org/toc/2158-3226The Faraday probe and cylindrical Langmuir probe were used to characterize the downstream ion and electron spatial evolution of a 300 W class low-power Hall thruster. The time-averaged ion current density, electron energy probability function, plasma potential, electron temperature, and electron density measurements were conducted at discharge voltages of 200–400 V and anode mass flow rates of 0.65 and 0.95 mg s−1 in the range of 100–500 mm axially and −100 to 100 mm radially downstream of the thruster. The results show that the ion and electron flows exhibit a bipolar diffusion characteristic along the radial direction. Meanwhile, the radial diffusion rate of ions in the plume is greater than the axial diffusion rate. The plasma potential decreases from 18 V at 100 mm axially from the thruster exit to 4 V at 500 mm axially and 100 mm radially. Correspondingly, the electron temperature decreases from 4.2 to 1.0 eV. The electron number density decreases from 2.6 × 1016 to 4 × 1014 m−3. A variable exponential relationship between electron temperature and electron density was observed from the measurements of electron energy probability distribution functions, with an adiabatic factor γ ranging between 1.3 and 1.4 (below the adiabatic value of 5/3). The adiabatic factor γ is considered to correlate with the anode mass flux and the spatial location of plasma, which suggests a possible dependence on the collision rate. These data are of great importance for plume model validation, improvement, plume effect evaluation, and protection mechanisms.Xinwei ChenJun GaoZuo GuNing GuoShangmin WangSanxiang YangYifan MaKai ShiHai GengHong ZhangYanxu PuAIP Publishing LLCarticlePhysicsQC1-999ENAIP Advances, Vol 11, Iss 11, Pp 115311-115311-10 (2021)
institution DOAJ
collection DOAJ
language EN
topic Physics
QC1-999
spellingShingle Physics
QC1-999
Xinwei Chen
Jun Gao
Zuo Gu
Ning Guo
Shangmin Wang
Sanxiang Yang
Yifan Ma
Kai Shi
Hai Geng
Hong Zhang
Yanxu Pu
Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster
description The Faraday probe and cylindrical Langmuir probe were used to characterize the downstream ion and electron spatial evolution of a 300 W class low-power Hall thruster. The time-averaged ion current density, electron energy probability function, plasma potential, electron temperature, and electron density measurements were conducted at discharge voltages of 200–400 V and anode mass flow rates of 0.65 and 0.95 mg s−1 in the range of 100–500 mm axially and −100 to 100 mm radially downstream of the thruster. The results show that the ion and electron flows exhibit a bipolar diffusion characteristic along the radial direction. Meanwhile, the radial diffusion rate of ions in the plume is greater than the axial diffusion rate. The plasma potential decreases from 18 V at 100 mm axially from the thruster exit to 4 V at 500 mm axially and 100 mm radially. Correspondingly, the electron temperature decreases from 4.2 to 1.0 eV. The electron number density decreases from 2.6 × 1016 to 4 × 1014 m−3. A variable exponential relationship between electron temperature and electron density was observed from the measurements of electron energy probability distribution functions, with an adiabatic factor γ ranging between 1.3 and 1.4 (below the adiabatic value of 5/3). The adiabatic factor γ is considered to correlate with the anode mass flux and the spatial location of plasma, which suggests a possible dependence on the collision rate. These data are of great importance for plume model validation, improvement, plume effect evaluation, and protection mechanisms.
format article
author Xinwei Chen
Jun Gao
Zuo Gu
Ning Guo
Shangmin Wang
Sanxiang Yang
Yifan Ma
Kai Shi
Hai Geng
Hong Zhang
Yanxu Pu
author_facet Xinwei Chen
Jun Gao
Zuo Gu
Ning Guo
Shangmin Wang
Sanxiang Yang
Yifan Ma
Kai Shi
Hai Geng
Hong Zhang
Yanxu Pu
author_sort Xinwei Chen
title Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster
title_short Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster
title_full Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster
title_fullStr Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster
title_full_unstemmed Spatial evolution characteristics of ion and electron flow for 300 W class low-power Hall thruster
title_sort spatial evolution characteristics of ion and electron flow for 300 w class low-power hall thruster
publisher AIP Publishing LLC
publishDate 2021
url https://doaj.org/article/f54a5b782d5c42dea853981529fd96d3
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